US20210122096A1 - Thin and light crack stopper with double extrusion plies - Google Patents
Thin and light crack stopper with double extrusion plies Download PDFInfo
- Publication number
- US20210122096A1 US20210122096A1 US16/664,162 US201916664162A US2021122096A1 US 20210122096 A1 US20210122096 A1 US 20210122096A1 US 201916664162 A US201916664162 A US 201916664162A US 2021122096 A1 US2021122096 A1 US 2021122096A1
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- United States
- Prior art keywords
- outer layer
- deicer
- ply
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- inch
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Images
Classifications
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- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C48/00—Extrusion moulding, i.e. expressing the moulding material through a die or nozzle which imparts the desired form; Apparatus therefor
- B29C48/001—Combinations of extrusion moulding with other shaping operations
- B29C48/0021—Combinations of extrusion moulding with other shaping operations combined with joining, lining or laminating
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
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- B29C48/00—Extrusion moulding, i.e. expressing the moulding material through a die or nozzle which imparts the desired form; Apparatus therefor
- B29C48/022—Extrusion moulding, i.e. expressing the moulding material through a die or nozzle which imparts the desired form; Apparatus therefor characterised by the choice of material
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
- B29C65/56—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using mechanical means or mechanical connections, e.g. form-fits
- B29C65/562—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using mechanical means or mechanical connections, e.g. form-fits using extra joining elements, i.e. which are not integral with the parts to be joined
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C66/00—General aspects of processes or apparatus for joining preformed parts
- B29C66/40—General aspects of joining substantially flat articles, e.g. plates, sheets or web-like materials; Making flat seams in tubular or hollow articles; Joining single elements to substantially flat surfaces
- B29C66/41—Joining substantially flat articles ; Making flat seams in tubular or hollow articles
- B29C66/43—Joining a relatively small portion of the surface of said articles
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- B32B25/00—Layered products comprising a layer of natural or synthetic rubber
- B32B25/04—Layered products comprising a layer of natural or synthetic rubber comprising rubber as the main or only constituent of a layer, which is next to another layer of the same or of a different material
- B32B25/08—Layered products comprising a layer of natural or synthetic rubber comprising rubber as the main or only constituent of a layer, which is next to another layer of the same or of a different material of synthetic resin
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- B—PERFORMING OPERATIONS; TRANSPORTING
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- B32B7/00—Layered products characterised by the relation between layers; Layered products characterised by the relative orientation of features between layers, or by the relative values of a measurable parameter between layers, i.e. products comprising layers having different physical, chemical or physicochemical properties; Layered products characterised by the interconnection of layers
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- B—PERFORMING OPERATIONS; TRANSPORTING
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- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
- B64D15/12—De-icing or preventing icing on exterior surfaces of aircraft by electric heating
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
- B64D15/16—De-icing or preventing icing on exterior surfaces of aircraft by mechanical means
- B64D15/166—De-icing or preventing icing on exterior surfaces of aircraft by mechanical means using pneumatic boots
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
- B29K2607/00—Use of natural rubber for preformed parts, e.g. for inserts
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
- B29L2031/3076—Aircrafts
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2605/00—Vehicles
- B32B2605/18—Aircraft
Definitions
- the present disclosure relates to deicers and, more particularly, to deicers with relatively thin and light outer layers.
- Conventional pneumatic deicers include a rubber surface ply which has a tendency to experience surface cracks. Such surface cracks may result from prolonged exposure to rain, ice, and debris impact, or by polymer degradation due to hydrolysis, ultraviolet radiation, ozone damage, or by repeated exposure to relatively low temperatures. The cracks may propagate laterally and vertically deep into an underlying rubber layer used to seal a fabric body. In response to the cracks reaching the fabric body, the pneumatic deicer may experience tubing inflation malfunctions.
- the method includes forming a body of the deicer.
- the method further includes forming an outer layer of the deicer through extrusion of an elastomeric material.
- the method further includes coupling the outer layer of the deicer to the body of the deicer.
- forming the outer layer of the deicer includes forming a first outer layer using the extrusion, forming a second outer layer using the extrusion, and coupling the first outer layer to the second outer layer.
- each of the first outer layer and the second outer layer are formed to have a thickness of between 2 thousandths of an inch (0.051 millimeters (mm)) and 40 thousandths of an inch (1.0 mm).
- each of the first outer layer and the second outer layer are formed to have the thickness of between 3 thousandths of an inch (0.076 mm) and 7 thousandths of an inch (0.18 mm).
- each of the first outer layer and the second outer layer are formed using a same material.
- any of the foregoing embodiments may further include forming a natural rubber gum ply, wherein coupling the outer layer of the deicer to the body of the deicer further includes coupling the natural rubber gum ply to the outer layer of the deicer and to the body of the deicer such that the natural rubber gum ply is located between the outer layer and the body.
- Any of the foregoing embodiments may further include forming a bond ply; and coupling the bond ply to the body such that the body is located between the bond ply and the natural rubber gum ply.
- the deicer is a pneumatic deicer and the body is configured to receive a gas to inflate the deicer.
- the deicer is an electrothermal deicer and the body is configured to receive electricity and convert the electricity into thermal energy.
- the outer layer includes an aliphatic polyether urethane.
- the method includes forming a body of the deicer.
- the method further includes forming a first outer layer and a second outer layer of the deicer through extrusion of an elastomeric material.
- the method further includes coupling the first outer layer to the second outer layer to form an outer layer of the deicer.
- the method further includes coupling the outer layer of the deicer to the body of the deicer.
- each of the first outer layer and the second outer layer are formed to have a thickness of between 2 thousandths of an inch (0.051 millimeters (mm)) and 40 thousandths of an inch (1.0 mm).
- each of the first outer layer and the second outer layer are formed to have the thickness of between 3 thousandths of an inch (0.076 mm) and 7 thousandths of an inch (0.18 mm).
- each of the first outer layer and the second outer layer are formed using a same material.
- any of the foregoing embodiments may further include forming a natural rubber gum ply, wherein coupling the outer layer of the deicer to the body of the deicer further includes coupling the natural rubber gum ply to the outer layer of the deicer and to the body of the deicer such that the natural rubber gum ply is located between the outer layer and the body.
- the deicer includes at least one of: a pneumatic deicer and the body is configured to receive a gas to inflate the deicer; or an electrothermal deicer and the body is configured to receive electricity and convert the electricity into thermal energy.
- the deicer configured for use in an aircraft.
- the deicer includes a body.
- the deicer further includes an outer layer coupled to the body and having a first outer layer and a second outer layer coupled together, each of the first outer layer and the second outer layer being formed using an extrusion process.
- each of the first outer layer and the second outer layer are formed from a same material, and formed to have a thickness of between 2 thousandths of an inch (0.051 millimeters (mm)) and 40 thousandths of an inch (1.0 mm).
- Any of the foregoing embodiments may further include a natural rubber gum ply located between the body and the outer layer.
- the deicer includes at least one of: a pneumatic deicer and the body is configured to receive a gas to inflate the deicer; or an electrothermal deicer and the body is configured to receive electricity and convert the electricity into thermal energy.
- FIG. 1 illustrates an aircraft including various components having an elastomeric outer layer, in accordance with various embodiments
- FIG. 2 is a flowchart illustrating a method for forming an aircraft component with an inner portion and an outer layer, in accordance with various embodiments
- FIG. 3A illustrates an aircraft component with an inner portion and an outer layer, in accordance with various embodiments
- FIG. 3B illustrates an aircraft component with an inner portion and an outer layer having multiple plies, according to various embodiments
- FIG. 4 illustrates a method for forming a deicer for use with an aircraft component, according to various embodiments
- FIG. 5 illustrates a pneumatic deicer for use with an aircraft component, according to various embodiments.
- FIG. 6 illustrates an electrothermal deicer for use with an aircraft component, according to various embodiments.
- any reference to singular includes plural embodiments, and any reference to more than one component or step may include a singular embodiment or step.
- any reference to attached, fixed, connected or the like may include permanent, removable, temporary, partial, full and/or any other possible attachment option.
- any reference to without contact (or similar phrases) may also include reduced contact or minimal contact. Surface shading lines may be used throughout the figures to denote different parts but not necessarily to denote the same or different materials.
- an aircraft 100 may include multiple aircraft components.
- the aircraft 100 may include a nosecone 102 , one or more wing 104 , one or more door 106 , a fuselage 108 , and one or more gas turbine engine 110 .
- these and other components of the aircraft 100 may include, or be coupled to, additional aircraft components.
- the nosecone 102 may include an erosion film 112 on an outer surface thereof
- the wing 104 may have a leading edge 114 with a pneumatic or electrothermal deicer 116
- the door 106 may have a seal 118 formed from a heated elastomer product 120 .
- Each of the erosion film 112 , the pneumatic or electrothermal deicer 116 , and the heated elastomer product 120 may have an inner portion which may face an interior of the component (e.g., the inner portion of the erosion film 112 may face the nosecone 102 , the inner portion of the pneumatic or electrothermal deicer 116 may face the wing 104 , and the inner portion of the heated elastomer product 120 may face the door 106 or the fuselage 108 ).
- Each of the erosion film 112 , the pneumatic or electrothermal deicer 116 , and the heated elastomer product 120 may further include an outer layer.
- the outer layer may be formed from, or may include, an elastomeric material and may be formed using an extrusion process.
- the outer layer may face an environment of the aircraft component.
- the outer portion of the erosion film may face oncoming air
- the outer portion of the electrothermal deicer 116 may face oncoming air
- the outer portion of the heated elastomer product 120 may face air in response to the door 106 being opened.
- extrusion to form an elastomeric outer layer may provide several benefits and advantages over forming an elastomeric outer layer using a conventional method.
- the use of extrusion allows the outer layer to be relatively thin, thus reducing weight of the aircraft component.
- extrusion allows for the formation of thinner layers, multiple layers may be stacked together to form a desired thickness of the total outer layer.
- the ability to stack multiple layers together provides benefits such as reducing the likelihood of defects (e.g., cracks, pores, or the like) extending through the outer layer, and simultaneously increasing the likelihood of uniformity of thickness of the outer layer.
- the use of extrusion results in a more robust product with an extended operating life and potentially having a lower weight, all desirable characteristics for aircraft components.
- the method 200 may begin in block 202 where an inner portion of the aircraft component is formed.
- the inner portion of the aircraft component may be formed using any method such as casting, forging, or the like.
- the inner portion may be formed to have any desirable shape including straight lines, angles, curves, or the like on at least one of edges or surfaces.
- the inner portion may include at least one of an adhesive, an elastomer, a rubber, a neoprene, a metal, or a woven fabric.
- one or more outer layer may be formed using an extrusion process.
- the outer layer may include an elastomeric material and may include one or multiple plies (i.e., multiple outer layers) coupled together.
- each of the multiple plies may be formed using the extrusion process.
- the extrusion process may include any type of extrusion such as blown extrusion or cast extrusion.
- the outer layer (whether one or multiple plies) may be formed to have a shape that corresponds to a shape of an outer surface of the inner portion.
- the outer layer may be formed via extrusion into a sheet structure and cut or otherwise reduced to a desired shape, or may be formed via extrusion to have a desired shape of the final outer layer.
- Blown extrusion which may be referred to as blown film extrusion, is a process of extrusion of molten materials and constant inflation of the material to several times its initial diameter. This may result in a thin, tubular product which may be slit to create a flat film.
- the extrusion may be done via an annular slit die, generally vertically, for the formation of a thin-walled tube.
- the introduction of air takes place through a hole present in the die's center for blowing up the tube just like a balloon.
- the cooling of the hot film is done by the high-speed air ring that blows onto it. This air ring is mounted on the top of die.
- Cast extrusion includes a molten polymer that travels through a flat die system to adopt its final flat film shape.
- the die system is formed by the die and feedblock (if the process requires coextrusion) or simply the die, if the process is that of mono-layer extrusion.
- the process starts with the feeding of plastic resins by means of a gravimetric feeding system to one or more extruders.
- the materials are then melted and mixed by the extruders, filtered and fed to the die system.
- the molten curtain enters the cooling unit where its temperature is lowered with a water-cooled chill roll to “freeze” the film.
- the film is then passed downstream where the edges are trimmed, corona treatment is applied (if a fabrication process such as printing or coating is required) and the film is wound into rolls.
- the one or more outer layer may be coupled to the inner portion.
- the one or more outer layer may be coupled to the inner portion using any technique such as adhesive, fasteners, an interference or press fit, or the like.
- an aircraft component 300 may include an inner portion 302 and an outer layer 304 .
- An adhesive 306 may be applied between the inner portion 302 and the outer layer 304 and used to couple the outer layer 304 to the inner portion 302 .
- the adhesive 306 resists separation of the outer layer 304 from the inner portion 302 .
- the adhesive may be heat-cured, chemically-cured, moisture-cured, anaerobic-cured, or the like.
- the outer layer 304 may be formed using an extrusion process.
- the outer layer 304 may be formed to have a relatively small thickness 308 .
- the total thickness of the outer layer 304 may be between 1 thousandths of an inch and 100 thousandths of an inch (0.025 millimeters (mm) and 2.5 mm), between 2 thousandths of an inch and 40 thousandths of an inch (0.051 mm and 1.0 mm), or between 2 thousandths of an inch and 20 thousandths of an inch (0.051 mm and 0.51 mm).
- the outer layer 304 may include a single ply.
- the material of the outer layer 304 may include any elastomeric material.
- the outer layer 304 may include a natural rubber, a synthetic rubber, a silicone, an elastomer, a thermoplastic, a thermoset, a polymeric material, or the like.
- the outer layer 304 is resistant to a relatively wide range of temperatures. Stated differently, use of the extrusion process results in the outer layer 304 retaining its physical properties in response to being exposed to a relatively wide range of temperatures.
- the outer layer 304 may be capable of retaining its physical properties in response to being exposed to temperatures between negative one hundred ( ⁇ 100) degrees Fahrenheit (F) and 350 degrees F. ( ⁇ 73.3 degrees Celsius (C) and 177 degrees C.), between ⁇ 70 degrees F. and 250 degrees F. ( ⁇ 57 degrees C. and 120 degrees C.), or between ⁇ 50 degrees F. and 200 degrees F. ( ⁇ 46 degrees C. and 93 degrees C.).
- another aircraft component 350 may include an inner portion 352 , an outer layer 354 , and one or more fasteners 356 .
- the outer layer 304 of FIG. 3A includes a single ply
- the outer layer 354 of FIG. 3B includes multiple plies, or multiple outer layers.
- the outer layer 354 includes a first outer layer 358 , a second outer layer 360 , and a third outer layer 362 stacked on top of each other.
- the fastener 356 may extend through each of the outer layers 358 , 360 , 362 and a portion of the inner portion 352 and may fasten each of the outer layers 358 , 360 , 362 the inner portion 352 together.
- an adhesive may be used in addition to, or instead of, the fastener 356 to couple each of the outer layers 358 , 360 , 362 together.
- Each of the outer layers 358 , 360 , 362 may be formed using an extrusion process, and may have the same or different thicknesses. Each of the outer layers 358 , 360 , 362 may be formed separately or at the same time using the extrusion process. In some embodiments, a single sheet of outer layer may be formed and may be cut into each of the outer layers 358 , 360 , 362 . In various embodiments, each of the outer layers 358 , 360 , 362 may be formed as separate parts. In various embodiments, each of the outer layers 358 , 360 , 362 may be formed from the same or different materials.
- each of the outer layers 358 , 360 , 362 may include a natural rubber, or the outer layers 358 , 360 may include a natural rubber and the outer layer 362 may include an elastomer.
- Each of the outer layers 358 , 360 may include any one or more of a natural rubber, a synthetic rubber, a silicone, an elastomer, a thermoplastic, a thermoset, a polymeric material, or the like.
- a thickness 364 of the each of the outer layers 358 , 360 , 362 may be between 1 thousandths of an inch and 100 thousandths of an inch (0.025 millimeters (mm) and 2.5 mm), between 2 thousandths of an inch and 40 thousandths of an inch (0.051 mm and 1.0 mm), or between 2 thousandths of an inch and 20 thousandths of an inch (0.051 mm and 0.51 mm). Additional outer layers may be added in order to achieve a desired thickness of the combined outer layer 354 .
- a defect in one of the outer layers is limited to that layer, and thus the defect is unlikely to extend through the entire outer layer (including the combination of outer layers 358 , 360 , 362 ).
- the method 400 may begin in block 402 where a body of the deicer is formed.
- the body which may also be referred to as a carcass, may be formed using any method such as casting, forging, weaving, sewing, or the like.
- the body may be designed to receive a fluid or gas and to inflate in response to receiving such fluid or gas.
- the deicer may be a pneumatic deicer.
- the body may be conductive and designed to convert electricity into thermal energy.
- the deicer may be an electrothermal deicer.
- the body may include any material such as an elastomeric material (e.g., a neoprene, an elastomer, or the like), a fabric material, or the like.
- an elastomeric material e.g., a neoprene, an elastomer, or the like
- a fabric material e.g., a fabric material, or the like.
- At least one outer layer may be formed using an extrusion process.
- the outer layer may include an elastomeric material such as a natural rubber, an elastomer, a plastic, a neoprene, a urethane, or the like.
- the outer layer may include an aliphatic polyether urethane with a relatively low glass transition temperature (Tg) and a relatively great resistance to ultraviolet light, ozone, and hydrolysis.
- the outer layer may include one, two, or more plies coupled together. In embodiments in which the outer layer includes two or more plies, each of the plies may be formed using the extrusion process.
- the extrusion process may include any type of extrusion such as blown extrusion or cast extrusion.
- the outer layer or layers may be formed to have a shape that corresponds to a shape of the body.
- the outer layer or layers may be formed via extrusion into a sheet structure and then cut or otherwise reduced to a desired shape, or may be formed via extrusion to have a desired shape of the final outer layer.
- a bond ply may be formed.
- the bond ply may be formed using any technique and may include any adhesive or other material usable to couple, attached, or fasten the deicer to an aircraft component, such as a wing, nosecone, propeller blade, or the like.
- the deicer may be coupled to the aircraft component using a liquid adhesive such that the bond ply is not separately formed.
- the bond ply may further include an elastomeric material such as a natural rubber, a neoprene, a urethane, or the like.
- a natural rubber gum ply may be formed.
- the natural rubber gum ply may be formed using any technique and may include a natural rubber.
- the natural rubber gum ply may include another elastomer such as a neoprene, a urethane, or the like.
- the bond ply and the natural rubber gum ply may seal the body.
- the body may be formed from a fabric material, and the bond ply and the natural rubber gum ply may, together with the body, form an airtight compartment for receiving a gas.
- a separate adhesive may be used to couple the bond ply to the aircraft component.
- the body, outer layer, bond ply, and natural rubber gum ply may be coupled together to form a deicer.
- These elements may be coupled together using any technique such as fasteners, one or more adhesive, or the like.
- the deicer may be coupled to a desired location on an aircraft component.
- the bond ply may be bonded to the desired location in order to fasten the deicer to the desired location on the component.
- a power source or a gas source may be coupled to the body.
- a gas source may be coupled to the body such that the gas source may provide gas to the body in order to inflate the body. In response to inflation of the body, any ice on the deicer may become cracked and removed from the deicer.
- a power source may be coupled to the body such that the power source may provide electricity to the body. In response to receiving the electricity, the deicer may convert the electricity into thermal energy which may in turn melt any ice located on the deicer.
- a pneumatic deicer 500 may be used as a deicer on an aircraft.
- the pneumatic deicer 500 may be formed using a method similar to the method 400 of FIG. 4 .
- the deicer 500 may include a body 502 , a bond ply 504 , a natural rubber gum ply 506 , and an outer layer 508 .
- the body 502 may include a first portion 514 , a second portion 516 , and a volume 518 therebetween.
- the volume 518 may be coupled to a gas source 506 such that the volume 518 may receive a gas from the gas source 506 .
- the body 502 may expand, thus shattering and removing any ice located on the deicer 500 .
- the bond ply 504 may include any adhesive or other material.
- the bond ply 504 may be coupled to an aircraft component, such as the nosecone 102 of FIG. 1 , in order to couple the deicer 500 to the aircraft component.
- the natural rubber gum ply 506 may include a natural rubber or other elastomer.
- the natural rubber gum ply 506 may be oriented such that the body 502 is located between the natural rubber gum ply 506 and the bond ply 504 .
- the body 502 may be formed from a porous material, such as a fabric.
- the bond ply 504 and the natural rubber gum ply 506 may seal the cavity 518 within the body 502 , thus reducing the likelihood of leakage of the gas from the body 502 .
- the bond ply 504 and the natural rubber gum ply 506 may be or may include non-porous materials capable of forming an airtight seal.
- the outer layer 508 may include a first ply 510 and a second ply 512 .
- the first ply 510 and the second ply 512 may each be formed using extrusion.
- the first ply 510 and the second ply 512 may be laminated together to form the outer layer 508 .
- Use of two plies provides various benefits and advantages. For example, any defect in the first ply 510 or the second ply 512 is unlikely to extend through the other of the first ply 510 or the second ply 512 .
- the first ply 510 will act as a crack stopper to reduce the likelihood of the crack extending into the body 502 and thus reducing the efficacy of the deicer 500 .
- the first ply 510 may have a first thickness 522
- the second ply 512 may have a second thickness 524 .
- the first thickness 522 and the second thickness 524 may be the same or different.
- the first thickness 522 and the second thickness 524 may be between 1 thousandths of an inch and 100 thousandths of an inch (0.025 mm and 2.5 mm), between 2 thousandths of an inch and 40 thousandths of an inch (0.051 mm and 1.0 mm), or between three thousandths of an inch and seven thousandths of an inch (0.076 mm and 0.18 mm).
- an electrothermal deicer 600 may have similar features as the pneumatic deicer 500 of FIG. 5 .
- the electrothermal deicer 600 may include a body 602 , a bond ply 604 , a natural rubber gum ply 606 , and an outer layer 608 .
- the bond ply 604 , natural rubber gum ply 606 , and outer layer 608 may be the same as, or similar to, the corresponding layers in the pneumatic deicer 500 of FIG. 5 .
- the body 602 may be formed from a conductive material, such as a metal, and may convert electricity into thermal energy (i.e., heat).
- a power source 620 may be coupled to the body 602 and may provide a voltage or current to the body 602 .
- the body 602 may generate thermal energy.
- any ice located on the electrothermal deicer 600 may melt.
- references to “various embodiments”, “one embodiment”, “an embodiment”, “an example embodiment”, etc. indicate that the embodiment described may include a particular feature, structure, or characteristic, but every embodiment may not necessarily include the particular feature, structure, or characteristic. Moreover, such phrases are not necessarily referring to the same embodiment. Further, when a particular feature, structure, or characteristic is described in connection with an embodiment, it is submitted that it is within the knowledge of one skilled in the art to affect such feature, structure, or characteristic in connection with other embodiments whether or not explicitly described. After reading the description, it will be apparent to one skilled in the relevant art(s) how to implement the disclosure in alternative embodiments.
Abstract
Description
- The present disclosure relates to deicers and, more particularly, to deicers with relatively thin and light outer layers.
- Conventional pneumatic deicers include a rubber surface ply which has a tendency to experience surface cracks. Such surface cracks may result from prolonged exposure to rain, ice, and debris impact, or by polymer degradation due to hydrolysis, ultraviolet radiation, ozone damage, or by repeated exposure to relatively low temperatures. The cracks may propagate laterally and vertically deep into an underlying rubber layer used to seal a fabric body. In response to the cracks reaching the fabric body, the pneumatic deicer may experience tubing inflation malfunctions.
- Disclosed herein is a method for forming a deicer. The method includes forming a body of the deicer. The method further includes forming an outer layer of the deicer through extrusion of an elastomeric material. The method further includes coupling the outer layer of the deicer to the body of the deicer.
- In any of the foregoing embodiments, forming the outer layer of the deicer includes forming a first outer layer using the extrusion, forming a second outer layer using the extrusion, and coupling the first outer layer to the second outer layer.
- In any of the foregoing embodiments, each of the first outer layer and the second outer layer are formed to have a thickness of between 2 thousandths of an inch (0.051 millimeters (mm)) and 40 thousandths of an inch (1.0 mm).
- In any of the foregoing embodiments, each of the first outer layer and the second outer layer are formed to have the thickness of between 3 thousandths of an inch (0.076 mm) and 7 thousandths of an inch (0.18 mm).
- In any of the foregoing embodiments, each of the first outer layer and the second outer layer are formed using a same material.
- Any of the foregoing embodiments may further include forming a natural rubber gum ply, wherein coupling the outer layer of the deicer to the body of the deicer further includes coupling the natural rubber gum ply to the outer layer of the deicer and to the body of the deicer such that the natural rubber gum ply is located between the outer layer and the body.
- Any of the foregoing embodiments may further include forming a bond ply; and coupling the bond ply to the body such that the body is located between the bond ply and the natural rubber gum ply.
- In any of the foregoing embodiments, the deicer is a pneumatic deicer and the body is configured to receive a gas to inflate the deicer.
- In any of the foregoing embodiments, the deicer is an electrothermal deicer and the body is configured to receive electricity and convert the electricity into thermal energy.
- In any of the foregoing embodiments, the outer layer includes an aliphatic polyether urethane.
- Also disclosed is a method for forming a deicer. The method includes forming a body of the deicer. The method further includes forming a first outer layer and a second outer layer of the deicer through extrusion of an elastomeric material. The method further includes coupling the first outer layer to the second outer layer to form an outer layer of the deicer. The method further includes coupling the outer layer of the deicer to the body of the deicer.
- In any of the foregoing embodiments, each of the first outer layer and the second outer layer are formed to have a thickness of between 2 thousandths of an inch (0.051 millimeters (mm)) and 40 thousandths of an inch (1.0 mm).
- In any of the foregoing embodiments, each of the first outer layer and the second outer layer are formed to have the thickness of between 3 thousandths of an inch (0.076 mm) and 7 thousandths of an inch (0.18 mm).
- In any of the foregoing embodiments, each of the first outer layer and the second outer layer are formed using a same material.
- Any of the foregoing embodiments may further include forming a natural rubber gum ply, wherein coupling the outer layer of the deicer to the body of the deicer further includes coupling the natural rubber gum ply to the outer layer of the deicer and to the body of the deicer such that the natural rubber gum ply is located between the outer layer and the body.
- In any of the foregoing embodiments, the deicer includes at least one of: a pneumatic deicer and the body is configured to receive a gas to inflate the deicer; or an electrothermal deicer and the body is configured to receive electricity and convert the electricity into thermal energy.
- Also disclosed is a deicer configured for use in an aircraft. The deicer includes a body. The deicer further includes an outer layer coupled to the body and having a first outer layer and a second outer layer coupled together, each of the first outer layer and the second outer layer being formed using an extrusion process.
- In any of the foregoing embodiments, each of the first outer layer and the second outer layer are formed from a same material, and formed to have a thickness of between 2 thousandths of an inch (0.051 millimeters (mm)) and 40 thousandths of an inch (1.0 mm).
- Any of the foregoing embodiments may further include a natural rubber gum ply located between the body and the outer layer.
- In any of the foregoing embodiments, the deicer includes at least one of: a pneumatic deicer and the body is configured to receive a gas to inflate the deicer; or an electrothermal deicer and the body is configured to receive electricity and convert the electricity into thermal energy.
- The foregoing features and elements may be combined in various combinations without exclusivity, unless expressly indicated otherwise. These features and elements as well as the operation thereof will become more apparent in light of the following description and the accompanying drawings. It should be understood, however, the following description and drawings are intended to be exemplary in nature and non-limiting.
- The subject matter of the present disclosure is particularly pointed out and distinctly claimed in the concluding portion of the specification. A more complete understanding of the present disclosure, however, may best be obtained by referring to the detailed description and claims when considered in connection with the figures, wherein like numerals denote like elements.
-
FIG. 1 illustrates an aircraft including various components having an elastomeric outer layer, in accordance with various embodiments; -
FIG. 2 is a flowchart illustrating a method for forming an aircraft component with an inner portion and an outer layer, in accordance with various embodiments; -
FIG. 3A illustrates an aircraft component with an inner portion and an outer layer, in accordance with various embodiments; -
FIG. 3B illustrates an aircraft component with an inner portion and an outer layer having multiple plies, according to various embodiments; -
FIG. 4 illustrates a method for forming a deicer for use with an aircraft component, according to various embodiments; -
FIG. 5 illustrates a pneumatic deicer for use with an aircraft component, according to various embodiments; and -
FIG. 6 illustrates an electrothermal deicer for use with an aircraft component, according to various embodiments. - The detailed description of exemplary embodiments herein makes reference to the accompanying drawings, which show exemplary embodiments by way of illustration. While these exemplary embodiments are described in sufficient detail to enable those skilled in the art to practice the exemplary embodiments of the disclosure, it should be understood that other embodiments may be realized and that logical changes and adaptations in design and construction may be made in accordance with this disclosure and the teachings herein. Thus, the detailed description herein is presented for purposes of illustration only and not limitation. The steps recited in any of the method or process descriptions may be executed in any order and are not necessarily limited to the order presented.
- Furthermore, any reference to singular includes plural embodiments, and any reference to more than one component or step may include a singular embodiment or step. Also, any reference to attached, fixed, connected or the like may include permanent, removable, temporary, partial, full and/or any other possible attachment option. Additionally, any reference to without contact (or similar phrases) may also include reduced contact or minimal contact. Surface shading lines may be used throughout the figures to denote different parts but not necessarily to denote the same or different materials.
- Referring now to
FIG. 1 , anaircraft 100 may include multiple aircraft components. For example, theaircraft 100 may include anosecone 102, one ormore wing 104, one ormore door 106, afuselage 108, and one or moregas turbine engine 110. These and other components of theaircraft 100 may include, or be coupled to, additional aircraft components. For example, thenosecone 102 may include anerosion film 112 on an outer surface thereof, thewing 104 may have a leadingedge 114 with a pneumatic orelectrothermal deicer 116, and thedoor 106 may have aseal 118 formed from a heatedelastomer product 120. Each of theerosion film 112, the pneumatic orelectrothermal deicer 116, and theheated elastomer product 120 may have an inner portion which may face an interior of the component (e.g., the inner portion of theerosion film 112 may face thenosecone 102, the inner portion of the pneumatic orelectrothermal deicer 116 may face thewing 104, and the inner portion of theheated elastomer product 120 may face thedoor 106 or the fuselage 108). Each of theerosion film 112, the pneumatic orelectrothermal deicer 116, and theheated elastomer product 120 may further include an outer layer. The outer layer may be formed from, or may include, an elastomeric material and may be formed using an extrusion process. In various embodiments, the outer layer may face an environment of the aircraft component. For example, the outer portion of the erosion film may face oncoming air, the outer portion of theelectrothermal deicer 116 may face oncoming air, and the outer portion of theheated elastomer product 120 may face air in response to thedoor 106 being opened. - Using extrusion to form an elastomeric outer layer may provide several benefits and advantages over forming an elastomeric outer layer using a conventional method. For example, the use of extrusion allows the outer layer to be relatively thin, thus reducing weight of the aircraft component. Because extrusion allows for the formation of thinner layers, multiple layers may be stacked together to form a desired thickness of the total outer layer. The ability to stack multiple layers together provides benefits such as reducing the likelihood of defects (e.g., cracks, pores, or the like) extending through the outer layer, and simultaneously increasing the likelihood of uniformity of thickness of the outer layer. Thus, the use of extrusion results in a more robust product with an extended operating life and potentially having a lower weight, all desirable characteristics for aircraft components.
- Turning to
FIG. 2 , amethod 200 for forming an aircraft component having an elastomeric surface or erosion ply is shown. Themethod 200 may begin inblock 202 where an inner portion of the aircraft component is formed. The inner portion of the aircraft component may be formed using any method such as casting, forging, or the like. The inner portion may be formed to have any desirable shape including straight lines, angles, curves, or the like on at least one of edges or surfaces. The inner portion may include at least one of an adhesive, an elastomer, a rubber, a neoprene, a metal, or a woven fabric. - In
block 204, one or more outer layer may be formed using an extrusion process. The outer layer may include an elastomeric material and may include one or multiple plies (i.e., multiple outer layers) coupled together. In embodiments in which the outer layer includes multiple plies, each of the multiple plies may be formed using the extrusion process. The extrusion process may include any type of extrusion such as blown extrusion or cast extrusion. The outer layer (whether one or multiple plies) may be formed to have a shape that corresponds to a shape of an outer surface of the inner portion. In some embodiments, the outer layer may be formed via extrusion into a sheet structure and cut or otherwise reduced to a desired shape, or may be formed via extrusion to have a desired shape of the final outer layer. - Blown extrusion, which may be referred to as blown film extrusion, is a process of extrusion of molten materials and constant inflation of the material to several times its initial diameter. This may result in a thin, tubular product which may be slit to create a flat film. The extrusion may be done via an annular slit die, generally vertically, for the formation of a thin-walled tube. The introduction of air takes place through a hole present in the die's center for blowing up the tube just like a balloon. The cooling of the hot film is done by the high-speed air ring that blows onto it. This air ring is mounted on the top of die.
- Cast extrusion includes a molten polymer that travels through a flat die system to adopt its final flat film shape. The die system is formed by the die and feedblock (if the process requires coextrusion) or simply the die, if the process is that of mono-layer extrusion. The process starts with the feeding of plastic resins by means of a gravimetric feeding system to one or more extruders. The materials are then melted and mixed by the extruders, filtered and fed to the die system. Immediately after exiting the die, the molten curtain enters the cooling unit where its temperature is lowered with a water-cooled chill roll to “freeze” the film. The film is then passed downstream where the edges are trimmed, corona treatment is applied (if a fabrication process such as printing or coating is required) and the film is wound into rolls.
- In
block 206, the one or more outer layer may be coupled to the inner portion. The one or more outer layer may be coupled to the inner portion using any technique such as adhesive, fasteners, an interference or press fit, or the like. - Referring to
FIG. 3A , anaircraft component 300 may include aninner portion 302 and anouter layer 304. An adhesive 306 may be applied between theinner portion 302 and theouter layer 304 and used to couple theouter layer 304 to theinner portion 302. In that regard, the adhesive 306 resists separation of theouter layer 304 from theinner portion 302. The adhesive may be heat-cured, chemically-cured, moisture-cured, anaerobic-cured, or the like. - The
outer layer 304 may be formed using an extrusion process. In that regard, theouter layer 304 may be formed to have a relativelysmall thickness 308. For example, the total thickness of theouter layer 304 may be between 1 thousandths of an inch and 100 thousandths of an inch (0.025 millimeters (mm) and 2.5 mm), between 2 thousandths of an inch and 40 thousandths of an inch (0.051 mm and 1.0 mm), or between 2 thousandths of an inch and 20 thousandths of an inch (0.051 mm and 0.51 mm). - The
outer layer 304 may include a single ply. The material of theouter layer 304 may include any elastomeric material. For example, theouter layer 304 may include a natural rubber, a synthetic rubber, a silicone, an elastomer, a thermoplastic, a thermoset, a polymeric material, or the like. - Use of the extrusion process results in the
outer layer 304 being resistant to a relatively wide range of temperatures. Stated differently, use of the extrusion process results in theouter layer 304 retaining its physical properties in response to being exposed to a relatively wide range of temperatures. For example, theouter layer 304 may be capable of retaining its physical properties in response to being exposed to temperatures between negative one hundred (−100) degrees Fahrenheit (F) and 350 degrees F. (−73.3 degrees Celsius (C) and 177 degrees C.), between −70 degrees F. and 250 degrees F. (−57 degrees C. and 120 degrees C.), or between −50 degrees F. and 200 degrees F. (−46 degrees C. and 93 degrees C.). - Turning to
FIG. 3B , anotheraircraft component 350 may include aninner portion 352, anouter layer 354, and one ormore fasteners 356. Whereas theouter layer 304 ofFIG. 3A includes a single ply, theouter layer 354 ofFIG. 3B includes multiple plies, or multiple outer layers. In particular, theouter layer 354 includes a firstouter layer 358, a secondouter layer 360, and a thirdouter layer 362 stacked on top of each other. Thefastener 356 may extend through each of theouter layers inner portion 352 and may fasten each of theouter layers inner portion 352 together. In various embodiments, an adhesive may be used in addition to, or instead of, thefastener 356 to couple each of theouter layers - Each of the
outer layers outer layers outer layers outer layers outer layers outer layers outer layers outer layer 362 may include an elastomer. Each of theouter layers - Use of the extrusion process allows each of the
outer layers thickness 364 of the each of theouter layers outer layer 354. Because of the separateouter layers outer layers - Referring now to
FIG. 4 , amethod 400 for forming a deicer having an elastomeric surface or erosion ply is shown. Themethod 400 may begin inblock 402 where a body of the deicer is formed. The body, which may also be referred to as a carcass, may be formed using any method such as casting, forging, weaving, sewing, or the like. In various embodiments, the body may be designed to receive a fluid or gas and to inflate in response to receiving such fluid or gas. In that regard, the deicer may be a pneumatic deicer. In various embodiments, the body may be conductive and designed to convert electricity into thermal energy. In that regard, the deicer may be an electrothermal deicer. - The body may include any material such as an elastomeric material (e.g., a neoprene, an elastomer, or the like), a fabric material, or the like.
- In
block 404, at least one outer layer may be formed using an extrusion process. The outer layer may include an elastomeric material such as a natural rubber, an elastomer, a plastic, a neoprene, a urethane, or the like. In various embodiments, the outer layer may include an aliphatic polyether urethane with a relatively low glass transition temperature (Tg) and a relatively great resistance to ultraviolet light, ozone, and hydrolysis. In various embodiments, the outer layer may include one, two, or more plies coupled together. In embodiments in which the outer layer includes two or more plies, each of the plies may be formed using the extrusion process. The extrusion process may include any type of extrusion such as blown extrusion or cast extrusion. The outer layer or layers may be formed to have a shape that corresponds to a shape of the body. In various embodiments, the outer layer or layers may be formed via extrusion into a sheet structure and then cut or otherwise reduced to a desired shape, or may be formed via extrusion to have a desired shape of the final outer layer. - In
block 406, a bond ply may be formed. The bond ply may be formed using any technique and may include any adhesive or other material usable to couple, attached, or fasten the deicer to an aircraft component, such as a wing, nosecone, propeller blade, or the like. In various embodiments, the deicer may be coupled to the aircraft component using a liquid adhesive such that the bond ply is not separately formed. In various embodiments, the bond ply may further include an elastomeric material such as a natural rubber, a neoprene, a urethane, or the like. - In
block 408, a natural rubber gum ply may be formed. The natural rubber gum ply may be formed using any technique and may include a natural rubber. In various embodiments, the natural rubber gum ply may include another elastomer such as a neoprene, a urethane, or the like. - In various embodiments, the bond ply and the natural rubber gum ply may seal the body. For example, the body may be formed from a fabric material, and the bond ply and the natural rubber gum ply may, together with the body, form an airtight compartment for receiving a gas. In that regard, a separate adhesive may be used to couple the bond ply to the aircraft component.
- In
block 410, the body, outer layer, bond ply, and natural rubber gum ply may be coupled together to form a deicer. These elements may be coupled together using any technique such as fasteners, one or more adhesive, or the like. - In
block 412, the deicer may be coupled to a desired location on an aircraft component. For example, the bond ply may be bonded to the desired location in order to fasten the deicer to the desired location on the component. - In
block 414, at least one of a power source or a gas source may be coupled to the body. In embodiments in which the deicer is a pneumatic deicer, a gas source may be coupled to the body such that the gas source may provide gas to the body in order to inflate the body. In response to inflation of the body, any ice on the deicer may become cracked and removed from the deicer. In embodiments in which the deicer is an electrothermal deicer, a power source may be coupled to the body such that the power source may provide electricity to the body. In response to receiving the electricity, the deicer may convert the electricity into thermal energy which may in turn melt any ice located on the deicer. - Referring now to
FIG. 5 , apneumatic deicer 500 may be used as a deicer on an aircraft. Thepneumatic deicer 500 may be formed using a method similar to themethod 400 ofFIG. 4 . Thedeicer 500 may include abody 502, abond ply 504, a naturalrubber gum ply 506, and anouter layer 508. - The
body 502 may include afirst portion 514, asecond portion 516, and avolume 518 therebetween. Thevolume 518 may be coupled to agas source 506 such that thevolume 518 may receive a gas from thegas source 506. In response to receiving the gas, thebody 502 may expand, thus shattering and removing any ice located on thedeicer 500. - The
bond ply 504 may include any adhesive or other material. Thebond ply 504 may be coupled to an aircraft component, such as thenosecone 102 ofFIG. 1 , in order to couple thedeicer 500 to the aircraft component. - The natural rubber gum ply 506 may include a natural rubber or other elastomer. The natural rubber gum ply 506 may be oriented such that the
body 502 is located between the naturalrubber gum ply 506 and thebond ply 504. - In various embodiments, the
body 502 may be formed from a porous material, such as a fabric. In that regard, thebond ply 504 and the natural rubber gum ply 506 may seal thecavity 518 within thebody 502, thus reducing the likelihood of leakage of the gas from thebody 502. In that regard, thebond ply 504 and the natural rubber gum ply 506 may be or may include non-porous materials capable of forming an airtight seal. - In various embodiments, the
outer layer 508 may include afirst ply 510 and asecond ply 512. Thefirst ply 510 and thesecond ply 512 may each be formed using extrusion. In various embodiments, thefirst ply 510 and thesecond ply 512 may be laminated together to form theouter layer 508. Use of two plies provides various benefits and advantages. For example, any defect in thefirst ply 510 or thesecond ply 512 is unlikely to extend through the other of thefirst ply 510 or thesecond ply 512. Additionally, if a crack forms in thesecond ply 512, then thefirst ply 510 will act as a crack stopper to reduce the likelihood of the crack extending into thebody 502 and thus reducing the efficacy of thedeicer 500. - The
first ply 510 may have afirst thickness 522, and thesecond ply 512 may have asecond thickness 524. Thefirst thickness 522 and thesecond thickness 524 may be the same or different. In various embodiments, thefirst thickness 522 and thesecond thickness 524 may be between 1 thousandths of an inch and 100 thousandths of an inch (0.025 mm and 2.5 mm), between 2 thousandths of an inch and 40 thousandths of an inch (0.051 mm and 1.0 mm), or between three thousandths of an inch and seven thousandths of an inch (0.076 mm and 0.18 mm). - Referring now to
FIG. 6 , anelectrothermal deicer 600 is shown. Theelectrothermal deicer 600 may have similar features as thepneumatic deicer 500 ofFIG. 5 . In particular, theelectrothermal deicer 600 may include abody 602, abond ply 604, a naturalrubber gum ply 606, and anouter layer 608. Thebond ply 604, naturalrubber gum ply 606, andouter layer 608 may be the same as, or similar to, the corresponding layers in thepneumatic deicer 500 ofFIG. 5 . - The
body 602 may be formed from a conductive material, such as a metal, and may convert electricity into thermal energy (i.e., heat). In that regard, apower source 620 may be coupled to thebody 602 and may provide a voltage or current to thebody 602. In response to receiving the voltage or current, thebody 602 may generate thermal energy. In response to thermal energy being generated by the body, any ice located on theelectrothermal deicer 600 may melt. - Benefits and other advantages have been described herein with regard to specific embodiments. Furthermore, the connecting lines shown in the various figures contained herein are intended to represent exemplary functional relationships and/or physical couplings between the various elements. It should be noted that many alternative or additional functional relationships or physical connections may be present in a practical system. However, the benefits, advantages, and any elements that may cause any benefit or advantage to occur or become more pronounced are not to be construed as critical, required, or essential features or elements of the disclosure. The scope of the disclosure is accordingly to be limited by nothing other than the appended claims, in which reference to an element in the singular is not intended to mean “one and only one” unless explicitly so stated, but rather “one or more.” Moreover, where a phrase similar to “at least one of A, B, or C” is used in the claims, it is intended that the phrase be interpreted to mean that A alone may be present in an embodiment, B alone may be present in an embodiment, C alone may be present in an embodiment, or that any combination of the elements A, B and C may be present in a single embodiment; for example, A and B, A and C, B and C, or A and B and C.
- Systems, methods and apparatus are provided herein. In the detailed description herein, references to “various embodiments”, “one embodiment”, “an embodiment”, “an example embodiment”, etc., indicate that the embodiment described may include a particular feature, structure, or characteristic, but every embodiment may not necessarily include the particular feature, structure, or characteristic. Moreover, such phrases are not necessarily referring to the same embodiment. Further, when a particular feature, structure, or characteristic is described in connection with an embodiment, it is submitted that it is within the knowledge of one skilled in the art to affect such feature, structure, or characteristic in connection with other embodiments whether or not explicitly described. After reading the description, it will be apparent to one skilled in the relevant art(s) how to implement the disclosure in alternative embodiments.
- Furthermore, no element, component, or method step in the present disclosure is intended to be dedicated to the public regardless of whether the element, component, or method step is explicitly recited in the claims. No claim element herein is to be construed under the provisions of 35 U.S.C. 112(f), unless the element is expressly recited using the phrase “means for.” As used herein, the terms “comprises”, “comprising”, or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.
Claims (20)
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EP20191227.6A EP3812276A1 (en) | 2019-10-25 | 2020-08-14 | Thin and light crack stopper with double extrusion plies |
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WO2015110974A1 (en) * | 2014-01-22 | 2015-07-30 | Zodiac Aerosafety Systems | De-icing system for aircraft |
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US4613102A (en) * | 1985-02-21 | 1986-09-23 | The B. F. Goodrich Company | Pneumatic deicers with template |
US8096508B2 (en) * | 2007-08-10 | 2012-01-17 | 3M Innovative Properties Company | Erosion resistant films for use on heated aerodynamic surfaces |
US8664573B2 (en) * | 2009-04-27 | 2014-03-04 | Applied Nanostructured Solutions, Llc | CNT-based resistive heating for deicing composite structures |
US9994325B2 (en) * | 2015-05-26 | 2018-06-12 | Goodrich Corporation | Polyether urethane deicer boots |
-
2019
- 2019-10-25 US US16/664,162 patent/US20210122096A1/en active Pending
-
2020
- 2020-08-14 EP EP20191227.6A patent/EP3812276A1/en active Pending
Patent Citations (2)
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EP0428011A2 (en) * | 1989-11-06 | 1991-05-22 | The B.F. Goodrich Company | Structural airfoil having integral expulsive system |
WO2015110974A1 (en) * | 2014-01-22 | 2015-07-30 | Zodiac Aerosafety Systems | De-icing system for aircraft |
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